Missile and hand held launcher



1969 e. KAYAIAN MISSILE AND HAND HELD LAUNCHER Sheet of 2 Filed Aug. 25.1967 INVENTOR. GEO/2'65 KAYAIAN BY W17. aw,

AGENT.

Jan. 14, 1969 G y MISSILE AND HAND HELD LAUNCHER Sheet Filed Aug. 25,1967 INVENT OR. GEORGE KAYA/AN AGE/V71,

United States Patent 3 Claims ABSTRACT OF THE DISCLOSURE This inventionis a hand held, tube launched, two-stage projectile adapted to be firedinitially by exploding a cartridge which propels the projectile out ofthe launching tube and ignites the main propellant in the projectile asafe distance from the launching location.

This invention relates generally to weapons and more particularly to anovel two-stage rocket and launcher.

Heretofore, hand held rocket launchers were generally of the singlestage type, i.e. an initial firing launched the missile toward itsintended target. The launcher or tube usually required a one man supportand aim plus a second man for loading. Aiming of the launcher waslimited to a substantially fiat trajectory in that the missilegravitationally rested within the tube in preparation for firing. Whenfired, the shock, recoil, or other physical effects associated with suchweapons was generated to a maximum condition as the missile leaves thelaunch tube. These effects limited the size of the firing charge in themissile and accordingly limited the distance that the missile traveledto its target.

The present invention employs a novel two-stage firing system thatinitially produces minor physical effects upon firing the first stage topropel the missile out of the launch tube and automatically ignites andfires the second stage when the missile is a safe distance from thelauncher.

Accordingly, one of the principal objects of the invention resides inthe provision of a launcher type rocket missile having a primarypropellant that when ignited ejects the missile from the launcher apredetermined distance and then automatically ignites the secondarypropellant which propels the missile to its target.

Another object of the invention is to provide in a rocket type launchermeans to secure the missile in firing position within the launch tube sothat the firing angle of the tube may be selectively varied withoutregard to accidental gravitational ejection of the missile.

Still another object of the invention is to provide a means toautomatically release said securing means upon the firing of the initialstage of the missile to permit normal egress of the missile from thetube.

Yet another object of the invention is to provide a second stageignition system that is ignited by the initial first stage firing systema predetermined period of time after said first stage is ignited and themissile has traveled out of the launch tube.

Other ancillary objects will be in part hereinafter apparent and will bein part hereinafter pointed out.

In the drawings:

FIGURE 1 is a side elevation of the rocket type missile with a portioncut away to illustrate the first stage propellant system.

FIGURE 2 is an enlarged cross-sectional detail of the first stage in itsstatic or pre-firing position.

FIGURE 3 is an enlarged cross-sectional detail of the first stage in itsfired position and prior to the ignition of the second stage propellantcharge.

FIGURE 4 is a perspective view taken from the rear of the missile with aportion cut away to more fully disclose the latching means that securesthe missile within the launch tube; and

FIGURE 5 is a rear view of the missile with the arrows representing thethrust gasses.

Referring to FIGURE 2 of the drawing in detail, 20 generally designatesthe launch tube having a through there 22, a reduced diametrical portion24 which forms an annular shoulder 26. Launch tube 20 is conventionaland need not be described in detail. Such tubes are well known to thoseskilled in the art. It is suificient to state that the tube 20 has afront orifice, not shown, through which the missile 30 will eject, aswill be hereinafter described.

Conversely, launch tube 20 has an enlarged diametrical portion 28 ofbore 22 adjacent to shoulder 26 that secures the missile 30 thereagainstwhen the missile 30 is loaded in the launch tube 20 for a purposehereinafter appearing.

Referring to FIGURES 1, 2, 3, 4, and 5, the missile 30, per se,comprises a cylindrical device having guidance fins 32 and 34. Thediametrical dimensions between opposite fins 32-34 is substantially thesame as the internal diameter of section 24 of bore 22.

Missile 30 comprises an initial firing section 36, a first propulsionsection 38, a main propulsion section 40 and a conventional war head 42with an impact fuse 44. Such fuses and war heads are conventional andwell known to those skilled in the art and need not be described indetail herein.

The section 36 comprises a conventional blank cartridge 46 disposedwithin a chamber 48 formed in a cylindrical block 50 that is centrallysecured in radial member 52. Member 52 is threadedly secured to theinner periphery 50 of missile 30. It will be noted that a thrust chamber56 surrounds the radial member 52 for purposes hereinafter appearing.Aflixed to block 50, FIG- URE 2, is a hollow tube 58 of similar diameterhaving a rear orifice 60 communicating with chamber 48, a forwardorifice 62 centrally located in the front wall 58a of tube 58, and apair of diametrically disposed exhaust ports 58b. Disposed within tube58 is .a hollow plunger 64 open at its rearmost end and secured to afuse member 66 at its closed forward end. Fuse member 66 projectsthrough orifice 62 in tube 58. Disposed within tube 58 andcircumjacently disposed around fuse member 66 is a spring 70, normallyurging plunger 64 rearwardly, such as shown in FIGURE 2.

When cartridge 46 is fired by conventional electrical means 72, thecharge in cartridge 46 ignites and the gasses produced thereby enterplunger 64 and drive said plunger forwardly, thus compressing spring 70,and driving fuse member 66 forwardly to engage said fuse member withmain propulsion section 40, as will be hereinafter apparent.Concurrently with the forward movement of plunger 64, latching means 74releases missile 30 from its secured position within launch tube 20.Latching means 74 comprise a pair of diametrically opposed pins 76 thatradially extend through radial member 52 and one pair of the rearmostfins 34. Pins 76 are urged inwardly by springs 78 and are retained intheir radially extended positions by their engagement with the outerperiphery of plunger 64 in its initial dormant position. With pins 76 intheir most extended position, said pins engage shoulder 26 of launchtube 20 and secure the missile 30 in the launch tube.

When the cartridge 46 is fired and plunger 64 moves forwardly, springs78 urge pins 76 radially inwardly releasing missile 30 from latchedposition within launch tube 20.

As previously set forth, the expanding gases generated by the explodingcartridge 46 drives plunger 64 forwardly 3 to the position shown inFIGURE 3 which exposes the exhaust ports 58b to the expanding gases.Further, as previously described, pins 76 are released from shoulder 26.Consequently, the released gases eject through thrust chamber 56 whichthrusts the missile 30- from launch tube 20.

When plunger 64 moved forwardly, the heat generated by the gases of theexploding cartridge 46 ignited the fuse member 66- which was furtherdriven into the main propulsion charge 40. Thus, after the missile 30has ejected from the launch tube 20' a safe distance, the fuse member 66ignites the main charge of propulsion section 40 which propels themissile 30 towards its intended target. The wall 80 of charge 40 beingexposed to thrust chamber'56' burns away and provides the thrustrequired to propel the missile after the initial thrust provided by thecartridge 46 has dissipated.

It will be noted that the latching pins 76 permit launch tube 20 to beaimed at any desired angle of trajectory without accidental dislodgingof the missile.

While there has been shown and described but a single embodiment of theinvention, it will be understood that changes and modifications could bemade without departing from the scope of the invention as set forth inthe following claims.

The invention claimed is:

1. A missile adapted to be fired from a manually held launch tubecomprising:

(a) an initial firing means adapted, when fired, to propel the missile asafe predetermined distance from the launch tube,

(b) a main propellant adapted to be ignited when said missile hastraveled the predetermined distance from the launch tube,

(c) latching means to secure the missile in the launch tube prior to theinitial firing to permit the launch tube to be aimed in any desiredmissile trajectory.

(d) said latching means comprises a pair of diametrically opposed pinsradially extending from the missile adapted to engage the innerperiphery of the launch tube,

(e) means to release said latching means upon the firing of the initialfiring means,

(f) a plunger movable by the gasses generated by said initial firingmeans adapted to engage and retain said diametrically opposed pins intheir respective radially extended position,

(g) spring means to urge said pins inwardly toward each other when saidplunger has moved, upon the firing of the initial firing means,

(11) and main propellant igniting means carried by said plunger andadapted to engage said main propellant upon movement of said plunger.

2. A missile adapted to be fired from a manually held launch tubecomprising:

(a) an initial firing means adapted, when fired, to propel the missile asafe predetermined distance from the launch tube,

(b) a main propellant adapted to be ignited when said missile hastraveled the predetermined distance from the launch tube,

(c) latching means to secure the missile in the launch tube prior to theinitial firing to permit the launch tube to be aimed in any desiredmissile trajectory.

(d) said latching means comprises a pair of diametrically opposed pinsradially extending from the missile adapted to engage the innerperiphery of the launch tube,

(e) means to release said latching means upon the firing of the initialfiring means,

(f) a plunger 'rnovable by the gasses generated by said initial firingmeans adapted to engage and retain said diametrically opposed pins intheir respective radially extended position,

(g) spring means to urge said pins inwardly toward each other when saidplunger has moved, upon the firing of the initial firing means,

(h) main propellant igniting means carried by said plunger and adaptedto engage said main propellant upon movement of said plunger,

(i) spring means normally retaining said plunger in its normal pinengaging position,

(j) and said spring means being compressible by the moving plunger whensaid plunger is moved by the gasses produced by the fired initial firingmeans.

3. A'missile adapted to be fired from a manually held launch tubecomprising:

(a) an initial firing means adapted, when fired, to propel the missile asafe predetermined distance from the launch tube,

(b) a main propellant adapted to be ignited when said missile hastraveled the predetermined distance from the launch tube, and

(c) latching means to secure the missile in the launch tube prior to theinitial firing to permit the launch tube to be aimed in any desiredmissile trajectory.

(d) said latching means comprises a pair of diametrically opposed pinsradially extending from the missile adapted to engage the innerperiphery of the launch tube,

(e) means to release said latching means upon the firing of the initialfiring means,

(f) a plunger movable by the gasses generated by said initial firingmeans adapted to engage and retain said diametrically opposed pins intheir respective radially extended position,

(g) spring means to urge said pins inwardly toward each other when saidplunger has moved, upon the firing of the initial firing means,

(h) main propellant igniting means carried by said plunger and adaptedto engage said main propellant upon movement of said plunger,

(i) spring means normally retaining said plunger in its normal pinengaging position,

(j) said spring means being compressible by the moving plunger when saidplunger is moved by the gasses produced by the fired initial firingmeans,

(k) fuse means carried by said plunger adapted to be ignited by thegasses generated by the firing of the initial firi-ng means,

(1) and said fuse means being adapted to engage the main propellant andignite said main propellant.

References Cited UNITED STATES PATENTS 2,788,712 4/1957 Ku-ller et al.89-1.807 2,944,486 7/1960 Vasse 10249.1 3,112,670 12/1963 Litz 89-l1.0113,139,795 7/1964 Altschuler 89-1.818 3,282,161 11/1966 Mac-Donald et al.89l.818

SAMUEL W. ENGLE, Primary Examiner.

US. Cl. X.R.

